US7874516B2 - Structural frame for an aircraft fuselage - Google Patents

Structural frame for an aircraft fuselage Download PDF

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Publication number
US7874516B2
US7874516B2 US11/718,845 US71884505A US7874516B2 US 7874516 B2 US7874516 B2 US 7874516B2 US 71884505 A US71884505 A US 71884505A US 7874516 B2 US7874516 B2 US 7874516B2
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United States
Prior art keywords
piece
cross
lower arch
structural frame
arch
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Expired - Fee Related, expires
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US11/718,845
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US20080093503A1 (en
Inventor
Bruno Cacciaguerra
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Airbus Operations SAS
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Airbus Operations SAS
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18—Floors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B64C1/062—Frames specially adapted to absorb crash loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to a structural frame for an aircraft fuselage producing a floor support suitable for receiving heavy loads whilst remaining low in weight.
  • the structures for aircraft fuselages comprise frames placed transversally at the axis of the fuselage, the lower portion of the frames being jointly called arch.
  • connection of cross-piece elements supporting a floor such as the floor of the hold of the aircraft on the frames is desirable.
  • the present invention is particularly suitable for producing structural frames for aircraft forming means supporting a floor of an aircraft, by constituting a structure provided with a metal arch and a composite cross-piece, the cross-piece forming the support for the floor.
  • the present invention mainly relates to a structural frame for a fuselage which comprises a lower arched structure, a cross-piece supporting a floor element and a connecting lattice between the lower arched structure and the cross-piece.
  • a connecting lattice comprising composite material bars the ends of which are spliced to the cross-piece and the lower arched structure enables the thermal exchanges between the shell of the fuselage and the cross-piece of the frame whereon are installed components (structures or systems) to be minimised.
  • FIG. 1 a front view of a structural frame of a fuselage according to the invention
  • FIGS. 2 a , 2 b perspective details of the frame from FIG. 1 ;
  • FIG. 3 a perspective view of the details of the lattice of the frame from FIG. 1 ;
  • FIG. 4 an enlarged front view of a lower portion of a frame element according to the invention
  • FIG. 5 a perspective view of two frames of a fuselage structure according to the invention.
  • FIG. 1 is an overall view of a structural frame of a fuselage comprising a lower arch 1 , a cross-piece 2 supporting a floor element 3 and a connecting lattice 4 between the lower arch 1 and the cross-piece 2 .
  • the upper frame element 5 is provided with arms 6 a , 6 b , 7 a , 7 b connecting with the cross-piece 2 and with the lower arch 1 .
  • the upper frame element 5 and the lower arch 1 form part of a frame of the structure of the fuselage.
  • connection arms 6 a , 6 b , 7 a , 7 b form a fork at each end of the upper frame 5 , the lower arch 1 and the cross-piece 2 being attached to the arms 6 a , 6 b , 7 a , 7 b of each fork via splicing.
  • the attachment of the arms to the cross-piece and to the lower arch is produced via splicing, an example being shown in FIG. 2 a for the attachment of the arm 6 a to one end of the cross-piece 2 .
  • the lower arch 1 and the cross-piece 2 are attached to the arms 6 a , 6 b , 7 a , 7 b of each fork via end-to-end splicing with the aid of splice plates 11 , 12 and bolts 13 .
  • the bars 4 are, as shown in FIG. 3 composite material beams with a U-shaped section, the cross-piece 2 itself also in composite materials, being produced according to said example in the form of a vertical web 2 a equipped with two longitudinal horizontal fabrics 2 b , 2 c of opposite directions placed on the lateral edges of the web 2 a , one of the fabrics may be provided on its free edge with a flattened lip 2 d opposing any twisting of the fabric 2 c.
  • the lower arch 1 may, like the cross-piece 2 , be a composite material arch but may also be a metal arch such as a machined aluminium arch.
  • the lower arch 1 is a metal arch
  • the latter is painted before attachment of the bars and the upper frame and a glass fabric crease 9 is placed between the ends of the bars 4 a , 4 b and the lower arch 1 to prevent any risk of corrosion at the interface between the bars and the lower arch.
  • the lower arch 1 is a ribbed beam provided with passage holes 10 for longitudinal stringers 8 supporting panels 14 of the fuselage.
  • FIG. 5 is a view of the embodiment of the structure of a segment of fuselage with the stringers 8 and longerons 16 connecting the frames.
  • the frames are placed spaced apart one behind the other along the structure of the fuselage and are of variable dimensions according to their longitudinal position and the shape of the fuselage.
  • the structural frame of the fuselage according to the invention is suitable for being produced with metal elements or by a mixed metal-composite structure, the composite lattice splicing on a metal or composite arch.
  • FIG. 4 shows an alternative embodiment for which the upper frame is of dissymmetric type and comprises at one of its ends a fork provided with arms 6 a , 6 b and at its other end a single attachment plate 15 , all of the arched structures, cross-piece and bars may be in composite material or at least one of the elements may be metal, the others being in composite material.

Abstract

A structural frame for a fuselage including a lower arched structure (1), a cross-piece (2), supporting a floor element (3) and a connecting lattice (4) between the lower arch (1) and the cross-piece (2), the connecting lattice (4) more particularly may comprise bars (4 a , 4 b) the ends of which are spliced to the cross-piece (2) and the lower arch (1).

Description

This application is the National Stage of International Application No. PCT/FR2005/050932, International Filing Date, 7 Nov. 2005, which designated the United States of America, and which international application was published under PCT Article 21(2) as WO Publication No. WO 2006/051235 and which claims priority from German Application No. 0452622, filed 15 Nov. 2004.
BACKGROUND
1. Field
The present invention relates to a structural frame for an aircraft fuselage producing a floor support suitable for receiving heavy loads whilst remaining low in weight.
2. Description of Related Developments
The structures for aircraft fuselages comprise frames placed transversally at the axis of the fuselage, the lower portion of the frames being jointly called arch.
To combat the tendency of the floor to deform in particular by pressurisation inside the cabin when the aircraft is in flight, the connection of cross-piece elements supporting a floor such as the floor of the hold of the aircraft on the frames is desirable.
SUMMARY
The present invention is particularly suitable for producing structural frames for aircraft forming means supporting a floor of an aircraft, by constituting a structure provided with a metal arch and a composite cross-piece, the cross-piece forming the support for the floor.
To do so, the present invention mainly relates to a structural frame for a fuselage which comprises a lower arched structure, a cross-piece supporting a floor element and a connecting lattice between the lower arched structure and the cross-piece.
Said configuration where the cross-piece is placed away from the lower arched structure and connected to said latter via a metal or composite lattice enables a frame with a very strong inertia and considerable height to be produced and said for the lowest possible weight and cost, the lower structure comprising the cross-piece, the lattice and the lower arch contributing to the overall stiffness of the frame.
Furthermore and according to one advantageous embodiment, the use of a connecting lattice comprising composite material bars the ends of which are spliced to the cross-piece and the lower arched structure enables the thermal exchanges between the shell of the fuselage and the cross-piece of the frame whereon are installed components (structures or systems) to be minimised.
DRAWINGS
Other characteristics and advantages of the invention will be better understood on reading the description which will follow of a non-limitative example of an embodiment of the invention in light of the figures which show:
FIG. 1; a front view of a structural frame of a fuselage according to the invention;
FIGS. 2 a, 2 b: perspective details of the frame from FIG. 1;
FIG. 3: a perspective view of the details of the lattice of the frame from FIG. 1;
FIG. 4: an enlarged front view of a lower portion of a frame element according to the invention
FIG. 5: a perspective view of two frames of a fuselage structure according to the invention.
 DESCRIPTION
FIG. 1 is an overall view of a structural frame of a fuselage comprising a lower arch 1, a cross-piece 2 supporting a floor element 3 and a connecting lattice 4 between the lower arch 1 and the cross-piece 2.
Said configuration where the cross-piece 2 is separated from the lower arch 1 and connected to said latter via a lattice 4 enables a frame with a very strong inertia and considerable height to be produced.
The lower structure including the cross-piece 2, the lattice 4, comprising bars 4 a, 4 b the ends of which are spliced to the lower arch 1 and the cross-piece 2, and, the lower arch 1 perfectly supports the floor and stiffens the entire frame, which is for example particularly suitable for a cargo aircraft configuration, the space between the cross-piece 2 and the lower arch 1 and the use of composite materials for the cross-piece 2 and the lattice 4 enabling the thermal exchanges between the shell of the fuselage and the cross-piece of the frame whereon are installed the components to be minimised.
For connecting the arch and the cross-piece, the upper frame element 5 is provided with arms 6 a, 6 b, 7 a, 7 b connecting with the cross-piece 2 and with the lower arch 1. The upper frame element 5 and the lower arch 1 form part of a frame of the structure of the fuselage.
According to the example in FIG. 1, the connection arms 6 a, 6 b, 7 a, 7 b form a fork at each end of the upper frame 5, the lower arch 1 and the cross-piece 2 being attached to the arms 6 a, 6 b, 7 a, 7 b of each fork via splicing.
The attachment of the arms to the cross-piece and to the lower arch is produced via splicing, an example being shown in FIG. 2 a for the attachment of the arm 6 a to one end of the cross-piece 2.
According to said example, the lower arch 1 and the cross-piece 2 are attached to the arms 6 a, 6 b, 7 a, 7 b of each fork via end-to-end splicing with the aid of splice plates 11, 12 and bolts 13.
In one preferred embodiment, the bars 4 are, as shown in FIG. 3 composite material beams with a U-shaped section, the cross-piece 2 itself also in composite materials, being produced according to said example in the form of a vertical web 2 a equipped with two longitudinal horizontal fabrics 2 b, 2 c of opposite directions placed on the lateral edges of the web 2 a, one of the fabrics may be provided on its free edge with a flattened lip 2 d opposing any twisting of the fabric 2 c.
The lower arch 1 may, like the cross-piece 2, be a composite material arch but may also be a metal arch such as a machined aluminium arch.
In the case where the lower arch 1 is a metal arch, the latter is painted before attachment of the bars and the upper frame and a glass fabric crease 9 is placed between the ends of the bars 4 a, 4 b and the lower arch 1 to prevent any risk of corrosion at the interface between the bars and the lower arch.
According to the example in FIG. 2 b, the lower arch 1 is a ribbed beam provided with passage holes 10 for longitudinal stringers 8 supporting panels 14 of the fuselage.
FIG. 5 is a view of the embodiment of the structure of a segment of fuselage with the stringers 8 and longerons 16 connecting the frames.
The frames are placed spaced apart one behind the other along the structure of the fuselage and are of variable dimensions according to their longitudinal position and the shape of the fuselage.
The structural frame of the fuselage according to the invention is suitable for being produced with metal elements or by a mixed metal-composite structure, the composite lattice splicing on a metal or composite arch.
The invention according to which all of the elements, arch, cross-piece frame and connecting lattice contribute to the stiffness of the assembly is not limited to the example shown and in particular FIG. 4 shows an alternative embodiment for which the upper frame is of dissymmetric type and comprises at one of its ends a fork provided with arms 6 a, 6 b and at its other end a single attachment plate 15, all of the arched structures, cross-piece and bars may be in composite material or at least one of the elements may be metal, the others being in composite material.

Claims (9)

1. A structural frame of a fuselage the frame comprising a lower arch, a cross-piece, supporting a floor element and a connecting lattice between the lower arch and the cross-piece, the frame further comprising an upper frame element provided with arms connecting with the cross-piece and with the lower arch.
2. A structural frame of a fuselage according to claim 1 wherein the connecting lattice comprises bars, the ends of which are spliced to the cross-piece and the lower arch.
3. A structural frame of a fuselage according to claim 2 wherein the bars are composite material beams with a U-shaped section.
4. A structural frame of a fuselage according to claim 1 wherein the connecting arms form a fork at each end of the upper frame, the lower arch and the cross-piece being attached to the arms of each fork via splicing.
5. A structural frame of a fuselage according to claim 4 wherein the lower arch and the cross-piece are attached to the arms of each fork via end-to-end splicing.
6. A structural frame of a fuselage according to claim 1 wherein the lower arch is a ribbed beam provided with passage holes for longitudinal stringers.
7. A structural frame of a fuselage according to claim 1 wherein the lower arch is a machined metal arch, a glass fabric crease being placed between the ends of the bars and the lower arch.
8. A structural frame of a fuselage according to claim 1, wherein the lower arch is a composite material arch.
9. A structural frame of a fuselage according to claim 1 comprising metal elements and elements made of composite material.
US11/718,845 2004-11-15 2005-11-07 Structural frame for an aircraft fuselage Expired - Fee Related US7874516B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0452622A FR2877916B1 (en) 2004-11-15 2004-11-15 AIRCRAFT FUSELAGE STRUCTURE FRAME
FR0452622 2004-11-15
PCT/FR2005/050932 WO2006051235A1 (en) 2004-11-15 2005-11-07 Structural frame for an aircraft fuselage

Publications (2)

Publication Number Publication Date
US20080093503A1 US20080093503A1 (en) 2008-04-24
US7874516B2 true US7874516B2 (en) 2011-01-25

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US (1) US7874516B2 (en)
EP (1) EP1812288B1 (en)
JP (1) JP4524313B2 (en)
CN (1) CN100546872C (en)
AT (1) ATE403598T1 (en)
BR (1) BRPI0517861A (en)
CA (1) CA2585869C (en)
DE (1) DE602005008765D1 (en)
FR (1) FR2877916B1 (en)
RU (1) RU2357892C2 (en)
WO (1) WO2006051235A1 (en)

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US20090314891A1 (en) * 2006-06-06 2009-12-24 Cord Haack Aircraft Fuselage Structure and Method for its Production
US20090321569A1 (en) * 2006-06-06 2009-12-31 Thorsten Schroeer Aircraft fuselage structure and method for its production
US20100065685A1 (en) * 2006-06-26 2010-03-18 Airbus Deutschland Gmbh Pressure bulkhead for an aerospace fuselage
US20100102171A1 (en) * 2008-10-27 2010-04-29 Osorio Silvio Luiz Francisco Aircraft cabin floor structures, systems and methods
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US8939404B2 (en) 2009-10-09 2015-01-27 Airbus Operations Gmbh Pressure fuselage of an aircraft with dome-shaped pressure bulkhead
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Cited By (26)

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US20090314891A1 (en) * 2006-06-06 2009-12-24 Cord Haack Aircraft Fuselage Structure and Method for its Production
US20090321569A1 (en) * 2006-06-06 2009-12-31 Thorsten Schroeer Aircraft fuselage structure and method for its production
US8695922B2 (en) 2006-06-06 2014-04-15 Airbus Operations Gmbh Aircraft fuselage structure and method for its production
US8651421B2 (en) * 2006-06-06 2014-02-18 Airbus Operations Gmbh Aircraft fuselage structure and method for its production
US20100181426A1 (en) * 2006-06-06 2010-07-22 Cord Haack Aircraft Fuselage Structure and Method for Producing it
US8534605B2 (en) 2006-06-06 2013-09-17 Airbus Operations Gmbh Aircraft fuselage structure and method for producing it
US8033503B2 (en) * 2006-06-26 2011-10-11 Airbus Deutschland Gmbh Pressure bulkhead for an aerospace fuselage
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EP1812288A1 (en) 2007-08-01
US20080093503A1 (en) 2008-04-24
CA2585869A1 (en) 2006-05-18
ATE403598T1 (en) 2008-08-15
EP1812288B1 (en) 2008-08-06
BRPI0517861A (en) 2008-10-21
JP2008519730A (en) 2008-06-12
RU2357892C2 (en) 2009-06-10
FR2877916B1 (en) 2008-04-25
CN100546872C (en) 2009-10-07
FR2877916A1 (en) 2006-05-19
RU2007122393A (en) 2008-12-20
CA2585869C (en) 2013-12-24
DE602005008765D1 (en) 2008-09-18
CN101056796A (en) 2007-10-17
JP4524313B2 (en) 2010-08-18
WO2006051235A1 (en) 2006-05-18

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